US10352190B2 - Cooling of an oil circuit of a turbomachine - Google Patents

Cooling of an oil circuit of a turbomachine Download PDF

Info

Publication number
US10352190B2
US10352190B2 US14/415,313 US201314415313A US10352190B2 US 10352190 B2 US10352190 B2 US 10352190B2 US 201314415313 A US201314415313 A US 201314415313A US 10352190 B2 US10352190 B2 US 10352190B2
Authority
US
United States
Prior art keywords
oil
turbomachine
refrigerant
condenser
heat exchanger
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US14/415,313
Other versions
US20150192033A1 (en
Inventor
Alain Pierre Garassino
Olivier Robert Michel Delepierre-Massue
Marc MISSOUT
Mathieu Jean Pierre Trohel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DELEPIERRE-MASSUE, OLIVIER ROBERT MICHEL, GARASSINO, ALAIN PIERRE, MISSOUT, MARC, TROHEL, MATHIEU JEAN PIERRE
Publication of US20150192033A1 publication Critical patent/US20150192033A1/en
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SNECMA
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Assignors: SNECMA
Application granted granted Critical
Publication of US10352190B2 publication Critical patent/US10352190B2/en
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
    • F01M5/00—Heating, cooling, or controlling temperature of lubricant; Lubrication means facilitating engine starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
    • F01M5/00—Heating, cooling, or controlling temperature of lubricant; Lubrication means facilitating engine starting
    • F01M5/002—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16N—LUBRICATING
    • F16N39/00—Arrangements for conditioning of lubricants in the lubricating system
    • F16N39/02—Arrangements for conditioning of lubricants in the lubricating system by cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B30/00—Heat pumps
    • F25B30/02—Heat pumps of the compression type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B1/00—Compression machines, plants or systems with non-reversible cycle
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y02T50/675—

Definitions

  • This invention relates to a turbomachine, such as a turbojet engine or a turboprop engine of an aircraft, comprising at least one oil circuit and means for cooling the oil of this circuit.
  • a turbomachine comprises an oil circuit for the lubrication of equipment, such as in particular roller bearings or members of gears, and also comprises a fuel circuit supplying injectors mounted in a combustion chamber.
  • an oil/fuel heat exchanger is used arranged in the oil and fuel circuits downstream or upstream of one or several oil/air heat exchanger(s) mounted in the oil circuit.
  • the oil/air heat exchanger is swept by an air flow coming from the exterior or interior of the turbomachine.
  • the oil/air heat exchanger is required to cool the oil when, for certain points of operation of the turbomachine, the oil/fuel heat exchanger does not make it possible to cool the oil sufficiently.
  • the oil/air heat exchanger is for example of the surface type, i.e. it comprises oil ducts swept by a flow of cold air coming from a bypass air flow called secondary air flow.
  • Such an exchanger is for example housed on a wall of the channel of the secondary flow, immediately downstream of the fan.
  • the oil/air heat exchanger can also be of the plate type and crossed by an air flow taken in the secondary air flow and reinjected at the outlet into the latter.
  • the difference in the temperature that can be used by the exchanger is reduced.
  • the temperature of the air is approximately 100° C. for example and the temperature of the oil not to be exceeded is for example approximately 150° C.
  • the exchanger must therefore operate with a temperature difference of hardly 50° C., which limits the performance of the heat exchanger.
  • the invention in particular has for purpose to provide a simple, effective and economical solution to this problem.
  • a turbomachine such as a turbojet engine or a turboprop engine of an aircraft, comprising at least one oil circuit and means for cooling the oil of this circuit, characterised in that the means for cooling comprise a thermodynamic refrigerant circuit provided with
  • the oil circuit is no longer cooled using a simple heat exchanger of the air/oil type but using a thermodynamic device of the heat pump type.
  • the heat is taken on the oil by the evaporator, then transferred to the air by the condenser, by the intermediary of the refrigerant.
  • temperature of the air of approximately 100° C.
  • the gain provided by the invention in terms of performance offsets the adding of the new elements comprising the heat pump and the disadvantages which are usually linked to such an addition (encumbrance, weight, etc.).
  • the turbomachine comprises a secondary stream for the passing of a secondary flow coming from a fan, with the first exchanger being arranged in the secondary stream.
  • the first exchanger is designed to exchange heat between the refrigerant and the ambient air, external to the turbomachine.
  • the oil circuit is designed to lubricate and/or cool elements of the motor of the turbomachine and/or a piece of equipment, such as an electric generator.
  • FIG. 1 is a diagrammatical view in perspective of a turbomachine of prior art
  • FIG. 2 is a partial diagrammatical view of an oil circuit of prior art
  • FIG. 3 is a view corresponding to FIG. 2 , illustrating a form of an embodiment of an oil circuit of a turbomachine, provided with a device of the heat pump type, in accordance with the invention.
  • FIG. 4 is a diagrammatical view of a heat exchanger configured to exchange heat between a refrigerant and an ambient air that is external to the turbomachine, in a non-limiting example.
  • FIG. 1 shows a turbomachine 1 of prior art comprising a combustion chamber 2 , with the combustion gases coming from the chamber driving a high-pressure turbine 3 and a low-pressure turbine 4 .
  • the high-pressure turbine 3 is coupled by a shaft to a high-pressure compressor arranged upstream of the combustion chamber 2 and supply the latter with air under pressure.
  • the low-pressure turbine 4 is coupled by another shaft to a fan wheel 5 arranged at the upstream end of the turbomachine 1 .
  • a transmission gearbox 6 or accessory case, is connected by a mechanical power tap 7 to the high-pressure turbine shaft 3 and comprises a set of drive pinions for the various pieces of equipment of the turbomachine, such as pumps and generators, in particular electrical. Other power transmissions can also be used.
  • FIG. 2 shows an oil circuit 8 of the turbomachine of FIG. 1 .
  • the oil circuit 8 comprises, from upstream to downstream in the direction in which the oil flows, various units 9 that use oil for lubrication and/or cooling, recovery pumps 10 allowing for the recirculation of oil from the pieces of equipment to a tank 11 , supply pumps 12 and a filter 13 .
  • the overall oil flow can comprise oil used for the lubrication of the accessory case and for the lubrication and cooling of one or several electric generators.
  • the oil circuit 8 comprises three heat exchangers mounted in series between the filter 13 and the units 9 , namely a main oil/fuel heat exchanger 14 , a secondary oil/fuel heat exchanger 15 and an oil/air heat exchanger 16 .
  • the oil/air heat exchanger 16 can be of the surface type, i.e. comprising oil ducts swept by a flow of cold air coming from a bypass air flow commonly referred to as secondary air flow. Such an exchanger 16 is for example housed on a wall of the channel of the secondary flow immediately downstream of the fan ( FIG. 1 ).
  • the oil/air heat exchanger 16 can be of the plate type and crossed by an air flow taken in the secondary air flow and reinjected at the outlet into the latter.
  • the air flow can be taken from the outside (ambient air).
  • a duct 17 is mounted in the oil circuit 8 as a bypass on the oil/air heat exchanger 16 and comprises an inlet arranged between the outlet of the filter 13 and the inlet of the oil/air heat exchanger 16 and an outlet arranged between the outlet of the oil/air heat exchanger 16 and the inlet of the secondary oil/fuel heat exchanger 15 .
  • a hydraulic valve 18 is mounted in the bypass line 17 and controls the passage of the oil flow in the oil/air exchanger 16 or through the bypass line 17 and the oil/air heat exchanger 16 . The oil exiting the main oil/fuel heat exchanger 14 then circulates to the oil tank 11 .
  • valve 18 opens in order to allow for the passing of oil through the bypass line 17 .
  • the currently used oil/air exchangers 16 have relatively low outputs which requires the use of relatively bulky exchangers. However, as the latter are placed in the secondary air flow, they generate aerodynamic disturbances which increase with their dimensions, which penalises the overall output of the turbomachine.
  • thermodynamic device 19 of the heat pump type.
  • this device 19 comprises a refrigerant circuit 20 provided with a first heat exchanger 21 able to exchange heat between the refrigerant and the air and forming a condenser, a second heat exchanger 22 able to exchange heat between the refrigerant and the oil of the oil circuit 8 and forming an evaporator, an expander 23 mounted downstream of the first exchanger 21 and upstream of the second exchanger 22 , in the direction in which the refrigerant circulates, and a compressor 24 mounted downstream of the second exchanger 22 and upstream of the first exchanger 21 .
  • the first exchanger 21 can be of the surface type (refrigerant ducts swept by a flow of air), or of the plate type.
  • a channel 25 passes a secondary flow 26 coming from a fan, with the first heat exchanger 21 that is a condenser arranged in the secondary flow 26 and housed on a wall 28 of the channel 25 , as shown in FIG. 3 .
  • the first heat exchanger 21 is configured to exchange heat between the refrigerant and ambient air 27 that is external to the turbomachine, as shown in FIG. 4 .
  • the compressor 24 is turned on.
  • the evaporator 22 then makes it possible to vaporise the refrigerant by taking heat on the oil.
  • the compressor 24 makes it possible to increase the pressure and the temperature of the refrigerant in vapour phase before the latter passes through the condenser 21 where it releases heat into to the air, by passing from the gaseous state to the liquid state.
  • the refrigerant in liquid phase then passes through the expander 23 which has for role to reduce its pressure and to lower its temperature, before passing through the evaporator 22 again.
  • Such a device is in general characterised by its coefficient of performance (COP) which can for example be of a magnitude of 5.
  • COP coefficient of performance
  • the size of the exchanger is limited by the fact that there can be exchanges between the refrigerant and the air with substantial differences in temperature.
  • thermodynamic device could be used in a turbomachine that has an oil circuit 8 with a structure different from that shown in FIG. 3 .

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A turbomachine or a turbojet engine or a turboprop engine of an aircraft, including at least one oil circuit and a cooling mechanism including a refrigerant circuit including a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser, a second heat exchanger configured to exchange heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander mounted downstream from the first exchanger and upstream from the second exchanger, in a direction in which the refrigerant circulates, and a compressor mounted downstream from the second exchanger and upstream from the first exchanger.

Description

This invention relates to a turbomachine, such as a turbojet engine or a turboprop engine of an aircraft, comprising at least one oil circuit and means for cooling the oil of this circuit.
In a known manner, a turbomachine comprises an oil circuit for the lubrication of equipment, such as in particular roller bearings or members of gears, and also comprises a fuel circuit supplying injectors mounted in a combustion chamber.
It is known to connect the oil and fuel circuits via heat exchangers with the purpose of avoiding a substantial heating of the lubrication oil, with the oil being cooled by exchange of heat with the fuel.
For this purpose, an oil/fuel heat exchanger is used arranged in the oil and fuel circuits downstream or upstream of one or several oil/air heat exchanger(s) mounted in the oil circuit. The oil/air heat exchanger is swept by an air flow coming from the exterior or interior of the turbomachine.
The oil/air heat exchanger is required to cool the oil when, for certain points of operation of the turbomachine, the oil/fuel heat exchanger does not make it possible to cool the oil sufficiently.
Other solutions are also known from prior art, as in particular the use of a thermostatic valve in a bypass line at the inlet of the oil/air heat exchanger or the use of sealing dampers for the supply with air.
Applications FR2951228, FR1061138 and FR1157953 of the Applicant describe architectures of oil and fuel circuits in a turbomachine.
The oil/air heat exchanger is for example of the surface type, i.e. it comprises oil ducts swept by a flow of cold air coming from a bypass air flow called secondary air flow. Such an exchanger is for example housed on a wall of the channel of the secondary flow, immediately downstream of the fan.
The oil/air heat exchanger can also be of the plate type and crossed by an air flow taken in the secondary air flow and reinjected at the outlet into the latter.
Current exchangers have relatively low outputs, which requires the use of exchangers that are relatively bulky. However, as the latter are placed in the secondary air flow, they generate aerodynamic disturbances which increase with their dimensions, which penalises the overall output of the turbomachine.
Furthermore, in the case of an oil/air exchanger for example, the difference in the temperature that can be used by the exchanger is reduced. By way of example, in certain operating phases of a turbojet engine, the temperature of the air is approximately 100° C. for example and the temperature of the oil not to be exceeded is for example approximately 150° C. The exchanger must therefore operate with a temperature difference of hardly 50° C., which limits the performance of the heat exchanger.
The invention in particular has for purpose to provide a simple, effective and economical solution to this problem.
To this effect, it proposes a turbomachine, such as a turbojet engine or a turboprop engine of an aircraft, comprising at least one oil circuit and means for cooling the oil of this circuit, characterised in that the means for cooling comprise a thermodynamic refrigerant circuit provided with
    • a first heat exchanger able to exchange heat between the refrigerant and the air and forming a condenser,
    • a second heat exchanger able to exchange heat between the refrigerant and the oil of the oil circuit and forming an evaporator,
    • an expander mounted downstream of the first exchanger and upstream of the second exchanger, in the direction in which the refrigerant circulates, and
    • a compressor mounted downstream of the second exchanger and upstream of the first exchanger.
In this way, the oil circuit is no longer cooled using a simple heat exchanger of the air/oil type but using a thermodynamic device of the heat pump type.
In this device, the heat is taken on the oil by the evaporator, then transferred to the air by the condenser, by the intermediary of the refrigerant. Using the preceding example (temperature of the air of approximately 100° C.), it is possible to bring the refrigerant to temperatures substantially higher than 150° C., in such a way as to be able to operate with a difference in temperature much greater than 50° C., which increases the effectiveness of the condenser and makes it possible in particular to limit the size of this condenser in such a way as to not affect the overall performance of the turbomachine.
Surprisingly, the gain provided by the invention in terms of performance offsets the adding of the new elements comprising the heat pump and the disadvantages which are usually linked to such an addition (encumbrance, weight, etc.).
Preferably, the turbomachine comprises a secondary stream for the passing of a secondary flow coming from a fan, with the first exchanger being arranged in the secondary stream.
Alternatively, the first exchanger is designed to exchange heat between the refrigerant and the ambient air, external to the turbomachine.
According to a characteristic of the invention, the oil circuit is designed to lubricate and/or cool elements of the motor of the turbomachine and/or a piece of equipment, such as an electric generator.
The invention shall be better understood and other details, characteristics and advantages of the invention shall appear when reading the following description given by way of a non-restricted example in reference to the annexed drawings wherein:
FIG. 1 is a diagrammatical view in perspective of a turbomachine of prior art;
FIG. 2 is a partial diagrammatical view of an oil circuit of prior art;
FIG. 3 is a view corresponding to FIG. 2, illustrating a form of an embodiment of an oil circuit of a turbomachine, provided with a device of the heat pump type, in accordance with the invention; and
FIG. 4 is a diagrammatical view of a heat exchanger configured to exchange heat between a refrigerant and an ambient air that is external to the turbomachine, in a non-limiting example.
FIG. 1 shows a turbomachine 1 of prior art comprising a combustion chamber 2, with the combustion gases coming from the chamber driving a high-pressure turbine 3 and a low-pressure turbine 4. The high-pressure turbine 3 is coupled by a shaft to a high-pressure compressor arranged upstream of the combustion chamber 2 and supply the latter with air under pressure. The low-pressure turbine 4 is coupled by another shaft to a fan wheel 5 arranged at the upstream end of the turbomachine 1.
A transmission gearbox 6, or accessory case, is connected by a mechanical power tap 7 to the high-pressure turbine shaft 3 and comprises a set of drive pinions for the various pieces of equipment of the turbomachine, such as pumps and generators, in particular electrical. Other power transmissions can also be used.
The FIG. 2 shows an oil circuit 8 of the turbomachine of FIG. 1.
The oil circuit 8 comprises, from upstream to downstream in the direction in which the oil flows, various units 9 that use oil for lubrication and/or cooling, recovery pumps 10 allowing for the recirculation of oil from the pieces of equipment to a tank 11, supply pumps 12 and a filter 13.
Other than the oil used for the lubrication and cooling of the turbomachine 1, in particular shaft bearings of turbines and of compressors, the overall oil flow can comprise oil used for the lubrication of the accessory case and for the lubrication and cooling of one or several electric generators.
The oil circuit 8 comprises three heat exchangers mounted in series between the filter 13 and the units 9, namely a main oil/fuel heat exchanger 14, a secondary oil/fuel heat exchanger 15 and an oil/air heat exchanger 16.
The oil/air heat exchanger 16 can be of the surface type, i.e. comprising oil ducts swept by a flow of cold air coming from a bypass air flow commonly referred to as secondary air flow. Such an exchanger 16 is for example housed on a wall of the channel of the secondary flow immediately downstream of the fan (FIG. 1).
Alternatively, the oil/air heat exchanger 16 can be of the plate type and crossed by an air flow taken in the secondary air flow and reinjected at the outlet into the latter. According to another alternative, the air flow can be taken from the outside (ambient air).
During operation, at the outlet of the supply pumps 12, the oil passes through the oil/air heat exchanger 16, the secondary oil/fuel heat exchanger 15 then the main oil/fuel heat exchanger 14. A duct 17 is mounted in the oil circuit 8 as a bypass on the oil/air heat exchanger 16 and comprises an inlet arranged between the outlet of the filter 13 and the inlet of the oil/air heat exchanger 16 and an outlet arranged between the outlet of the oil/air heat exchanger 16 and the inlet of the secondary oil/fuel heat exchanger 15. A hydraulic valve 18 is mounted in the bypass line 17 and controls the passage of the oil flow in the oil/air exchanger 16 or through the bypass line 17 and the oil/air heat exchanger 16. The oil exiting the main oil/fuel heat exchanger 14 then circulates to the oil tank 11.
In cold operating conditions, the valve 18 opens in order to allow for the passing of oil through the bypass line 17.
As indicated hereinabove, the currently used oil/air exchangers 16 have relatively low outputs which requires the use of relatively bulky exchangers. However, as the latter are placed in the secondary air flow, they generate aerodynamic disturbances which increase with their dimensions, which penalises the overall output of the turbomachine.
In order to avoid this, the invention propose to replace the oil/air exchanger 16 with a thermodynamic device 19 of the heat pump type. As is shown in FIG. 3, this device 19 comprises a refrigerant circuit 20 provided with a first heat exchanger 21 able to exchange heat between the refrigerant and the air and forming a condenser, a second heat exchanger 22 able to exchange heat between the refrigerant and the oil of the oil circuit 8 and forming an evaporator, an expander 23 mounted downstream of the first exchanger 21 and upstream of the second exchanger 22, in the direction in which the refrigerant circulates, and a compressor 24 mounted downstream of the second exchanger 22 and upstream of the first exchanger 21.
The first exchanger 21 can be of the surface type (refrigerant ducts swept by a flow of air), or of the plate type. In a non-limiting example, a channel 25 passes a secondary flow 26 coming from a fan, with the first heat exchanger 21 that is a condenser arranged in the secondary flow 26 and housed on a wall 28 of the channel 25, as shown in FIG. 3. In another non-limiting example, the first heat exchanger 21 is configured to exchange heat between the refrigerant and ambient air 27 that is external to the turbomachine, as shown in FIG. 4.
During operation, when it is necessary to cool the oil of the circuit 8, the compressor 24 is turned on. The evaporator 22 then makes it possible to vaporise the refrigerant by taking heat on the oil. The compressor 24 makes it possible to increase the pressure and the temperature of the refrigerant in vapour phase before the latter passes through the condenser 21 where it releases heat into to the air, by passing from the gaseous state to the liquid state. The refrigerant in liquid phase then passes through the expander 23 which has for role to reduce its pressure and to lower its temperature, before passing through the evaporator 22 again.
Such a device is in general characterised by its coefficient of performance (COP) which can for example be of a magnitude of 5. This means that, for one unit of energy brought to the compressor 24 (in the form of electrical energy), 5 units of energy (in the form of heat) are taken from the oil and transferred to the air.
The very good output of such a device 19 therefore makes it possible to limit the size of the exchanger 21 between the air and the refrigerant, in such a way as to not substantially affect the output of the turbomachine.
In particular, the size of the exchanger is limited by the fact that there can be exchanges between the refrigerant and the air with substantial differences in temperature.
Of course, such a thermodynamic device could be used in a turbomachine that has an oil circuit 8 with a structure different from that shown in FIG. 3.

Claims (13)

The invention claimed is:
1. A turbomachine, or a turbojet engine or a turboprop engine of an aircraft, comprising:
at least one oil circuit; and
a thermodynamic refrigerant circuit to cool oil of the at least one oil circuit, comprising:
a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser,
a second heat exchanger configured to exchange heat between the refrigerant and the oil of the at least one oil circuit and forming an evaporator,
an expander mounted downstream of the condenser and upstream of the evaporator, in a direction in which the refrigerant circulates, and
a compressor mounted downstream of the evaporator and upstream of the condenser,
wherein the condenser is configured to exchange heat between the refrigerant and ambient air that is external to the turbomachine,
wherein the at least one oil circuit is configured to lubricate and/or cool elements of a motor of the turbomachine and/or an electric generator,
wherein the at least one oil circuit comprises a recovery pump, a tank, a supply pump, a filter, and an oil/fuel heat exchanger,
wherein the at least one oil circuit passes the oil in a flow direction from upstream to downstream through at least one structure that uses the oil, the recovery pump, the tank, the supply pump, the filter, and the oil/fuel heat exchanger in this listed order, and
wherein a portion of the at least one oil circuit that passes the oil through the evaporator is positioned upstream in the flow direction from the oil/fuel heat exchanger.
2. The turbomachine according to claim 1, wherein the thermodynamic refrigerant circuit has a coefficient of performance (COP) of a magnitude of 5.
3. The turbomachine according to claim 1, wherein the evaporator transfers heat from the oil to the refrigerant to bring the refrigerant to a temperature higher than 150° C.
4. The turbomachine according to claim 1, further comprising a channel to pass a secondary flow coming from a fan of the turbomachine, and wherein
the condenser is arranged in the secondary flow in the channel to release heat to the air by passing the refrigerant received by the condenser in a gaseous state to a liquid state.
5. The turbomachine according to claim 4, wherein the secondary flow is a bypass air flow coming from the fan of the turbomachine.
6. The turbomachine according to claim 4, wherein the condenser is housed on a wall of the channel that passes the secondary flow coming from the fan of the turbomachine.
7. The turbomachine according to claim 1, wherein the at least one oil circuit is configured to lubricate and/or cool elements of the electric generator.
8. A turbomachine, or a turbojet engine or a turboprop engine of an aircraft, comprising:
at least one oil circuit;
a channel to pass a secondary flow coming from a fan of the turbomachine; and
a thermodynamic refrigerant circuit to cool oil of the at least one oil circuit, comprising:
a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser, and the condenser is arranged in the secondary flow in the channel to release heat to the air by passing the refrigerant received by the condenser in a gaseous state to a liquid state,
a second heat exchanger configured to exchange heat between the refrigerant and the oil of the at least one oil circuit and forming an evaporator,
an expander mounted downstream of the condenser and upstream of the evaporator, in a direction in which the refrigerant circulates, and
a compressor mounted downstream of the evaporator and upstream of the condenser,
wherein the at least one oil circuit comprises a recovery pump, a tank, a supply pump, a filter, and an oil/fuel heat exchanger,
wherein the at least one oil circuit passes the oil in a flow direction from upstream to downstream through at least one structure that uses the oil, the recovery pump, the tank, the supply pump, the filter, and the oil/fuel heat exchanger in this listed order, and
wherein a portion of the at least one oil circuit that passes the oil through the evaporator is positioned upstream in the flow direction from the oil/fuel heat exchanger.
9. The turbomachine according to claim 8, wherein the at least one oil circuit is configured to lubricate and/or cool elements of a motor of the turbomachine and/or an electric generator.
10. The turbomachine according to claim 8, wherein the secondary flow is a bypass air flow coming from the fan of the turbomachine.
11. The turbomachine according to claim 8, wherein the condenser is housed on a wall of the channel that passes the secondary flow coming from the fan of the turbomachine.
12. The turbomachine according to claim 8, wherein the thermodynamic refrigerant circuit has a coefficient of performance (COP) of a magnitude of 5.
13. The turbomachine according to claim 8, wherein the evaporator transfers heat from the oil to the refrigerant to bring the refrigerant to a temperature higher than 150° C.
US14/415,313 2012-07-19 2013-07-12 Cooling of an oil circuit of a turbomachine Active 2034-10-15 US10352190B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1257015 2012-07-19
FR1257015A FR2993610B1 (en) 2012-07-19 2012-07-19 COOLING THE OIL CIRCUIT OF A TURBOMACHINE
PCT/FR2013/051680 WO2014013170A1 (en) 2012-07-19 2013-07-12 Cooling of an oil circuit of a turbomachine

Publications (2)

Publication Number Publication Date
US20150192033A1 US20150192033A1 (en) 2015-07-09
US10352190B2 true US10352190B2 (en) 2019-07-16

Family

ID=46963910

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/415,313 Active 2034-10-15 US10352190B2 (en) 2012-07-19 2013-07-12 Cooling of an oil circuit of a turbomachine

Country Status (4)

Country Link
US (1) US10352190B2 (en)
FR (1) FR2993610B1 (en)
GB (1) GB2519016B (en)
WO (1) WO2014013170A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200332714A1 (en) * 2019-04-17 2020-10-22 United Technologies Corporation Integrated thermal management system for fuel cooling

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3027624B1 (en) * 2014-10-27 2019-04-19 Safran Aircraft Engines CIRCUIT FOR DEFROSTING AIR INLET LIP FROM A PROPELLANT AIRCRAFT ASSEMBLY
FR3034464B1 (en) * 2015-04-03 2017-03-24 Snecma COOLING THE OIL CIRCUIT OF A TURBOMACHINE
US10087777B2 (en) * 2016-04-29 2018-10-02 Hamilton Sundstrand Corporation Lubricant cooling systems for high speed turbomachines
FR3051509B1 (en) 2016-05-20 2018-06-15 Safran REVERSIBLE SYSTEM FOR DISSIPATING THERMAL POWER GENERATED IN A GAS TURBINE ENGINE
FR3056641B1 (en) 2016-09-23 2020-06-12 Safran SYSTEM FOR COOLING A CIRCUIT OF A FIRST FLUID OF A TURBOMACHINE
US11028775B2 (en) * 2018-08-23 2021-06-08 The Boeing Company Bleed air boosted engine oil cooler
FR3094744B1 (en) * 2019-04-03 2021-12-10 Safran Nacelles Coolant for aircraft turbojet cooling system
FR3094749B1 (en) * 2019-04-03 2021-11-19 Safran Nacelles Aircraft turbojet cooling system
FR3094750B1 (en) * 2019-04-03 2021-11-26 Safran Nacelles Aircraft turbojet cooling system
US11638889B2 (en) * 2019-09-25 2023-05-02 Pratt & Whitney Canada Corp. Filter cover protection against external contamination
CN112879788A (en) * 2021-01-22 2021-06-01 宁波云德半导体材料有限公司 External quartz machining center lubricating liquid cooling system device
GB2622208A (en) * 2022-09-06 2024-03-13 Rolls Royce Plc A thermal management system for an aircraft
GB2622212B (en) 2022-09-06 2024-11-20 Rolls Royce Plc A thermal management system for an aircraft
GB2622209B (en) 2022-09-06 2024-12-04 Rolls Royce Plc A thermal management system for an aircraft
GB2622214A (en) 2022-09-06 2024-03-13 Rolls Royce Plc A thermal management system for an aircraft
GB2622211A (en) * 2022-09-06 2024-03-13 Rolls Royce Plc A thermal management system for an aircraft
GB2622215B (en) 2022-09-06 2024-12-04 Rolls Royce Plc A thermal management system for an aircraft
GB202219390D0 (en) * 2022-12-21 2023-02-01 Rolls Royce Plc Gas turbine operation
FR3154148B1 (en) 2023-10-13 2025-10-03 Safran Aircraft Engines METHOD FOR HEATING THE FUEL OF A FUEL SUPPLY SYSTEM OF A TURBOMACHINE
FR3154147A1 (en) 2023-10-13 2025-04-18 Safran Aircraft Engines AIRCRAFT TURBOMACHINE COMPRISING A HEAT PUMP
FR3154146A1 (en) 2023-10-13 2025-04-18 Safran Aircraft Engines AIRCRAFT TURBOMACHINE COMPRISING A HEAT PUMP
GB202319139D0 (en) * 2023-12-14 2024-01-31 Rolls Royce Plc Gas turbine engine flow management

Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2979293A (en) * 1956-03-02 1961-04-11 Jay A Mount Cooling for supersonic aircraft
US3705496A (en) * 1963-11-20 1972-12-12 Texaco Experiment Inc Reaction propulsion engine and method of operation
US4151710A (en) * 1977-03-11 1979-05-01 United Technologies Corporation Lubrication cooling system for aircraft engine accessory
US4254618A (en) * 1977-08-18 1981-03-10 General Electric Company Cooling air cooler for a gas turbofan engine
US4273304A (en) * 1979-01-31 1981-06-16 Frosch Robert A Cooling system for high speed aircraft
US4474001A (en) * 1981-04-01 1984-10-02 United Technologies Corporation Cooling system for the electrical generator of a turbofan gas turbine engine
US4505124A (en) * 1983-09-22 1985-03-19 The United States Of America As Represented By The Secretary Of The Air Force Heat management system for aircraft
US4773212A (en) * 1981-04-01 1988-09-27 United Technologies Corporation Balancing the heat flow between components associated with a gas turbine engine
US5121599A (en) * 1991-02-21 1992-06-16 United Technologies Corporation Oil filtration system and method
US6182435B1 (en) * 1997-06-05 2001-02-06 Hamilton Sundstrand Corporation Thermal and energy management method and apparatus for an aircraft
US6948331B1 (en) * 2003-09-12 2005-09-27 Norhrop Grumman Corporation Environmental control system for an aircraft
US20060005547A1 (en) * 2004-07-09 2006-01-12 David Brouillet Cooling arrangement for an accessory gearbox and method of cooling
US20070256421A1 (en) * 2006-05-04 2007-11-08 Dooley Kevin A Gas turbine engine oil system operation
EP1895124A2 (en) 2006-08-31 2008-03-05 General Electric Company Oil cooling apparatus in fan cowling and method therefor
US7377100B2 (en) * 2004-08-27 2008-05-27 Pratt & Whitney Canada Corp. Bypass duct fluid cooler
FR2914365A1 (en) 2007-03-28 2008-10-03 Airbus France Sas Equipment e.g. electric generator, cooling and controlling system for propulsion system i.e. jet engine, of aircraft, has closed circuit circulating heat transfer fluid between equipments and two heat exchange units
WO2009140100A1 (en) 2008-05-13 2009-11-19 General Electric Company Method and apparatus for controlling fuel in a gas turbine engine
WO2010051011A1 (en) 2008-11-03 2010-05-06 Smith J Walter Systems and methods for thermal management in a gas turbine powerplant
US7861512B2 (en) * 2006-08-29 2011-01-04 Pratt & Whitney Canada Corp. Turbofan bypass duct air cooled fluid cooler installation
US8522572B2 (en) * 2010-07-01 2013-09-03 General Electric Company Adaptive power and thermal management system
US20140140829A1 (en) * 2012-11-16 2014-05-22 United Technologies Corporation Turbine engine cooling system with an open loop circuit
US8789376B2 (en) * 2011-05-27 2014-07-29 General Electric Company Flade duct turbine cooling and power and thermal management
US8967531B2 (en) * 2011-03-28 2015-03-03 Rolls-Royce Corporation Aircraft and airborne electrical power and thermal management system
US9254920B2 (en) * 2012-05-30 2016-02-09 General Electric Company Aircraft energy management system including engine fan discharge air boosted environmental control system
WO2016156756A1 (en) * 2015-04-03 2016-10-06 Snecma Cooling of a turbine engine oil circuit
US20180050810A1 (en) * 2016-08-19 2018-02-22 General Electric Company Propulsion engine for an aircraft
US20180050811A1 (en) * 2016-08-19 2018-02-22 General Electric Company Propulsion engine for an aircraft

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8757086B2 (en) * 2010-07-28 2014-06-24 Randel Brandstrom Cladding the interior of a straight pipe section

Patent Citations (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2979293A (en) * 1956-03-02 1961-04-11 Jay A Mount Cooling for supersonic aircraft
US3705496A (en) * 1963-11-20 1972-12-12 Texaco Experiment Inc Reaction propulsion engine and method of operation
US4151710A (en) * 1977-03-11 1979-05-01 United Technologies Corporation Lubrication cooling system for aircraft engine accessory
US4254618A (en) * 1977-08-18 1981-03-10 General Electric Company Cooling air cooler for a gas turbofan engine
US4273304A (en) * 1979-01-31 1981-06-16 Frosch Robert A Cooling system for high speed aircraft
US4474001A (en) * 1981-04-01 1984-10-02 United Technologies Corporation Cooling system for the electrical generator of a turbofan gas turbine engine
US4773212A (en) * 1981-04-01 1988-09-27 United Technologies Corporation Balancing the heat flow between components associated with a gas turbine engine
US4505124A (en) * 1983-09-22 1985-03-19 The United States Of America As Represented By The Secretary Of The Air Force Heat management system for aircraft
US5121599A (en) * 1991-02-21 1992-06-16 United Technologies Corporation Oil filtration system and method
US6182435B1 (en) * 1997-06-05 2001-02-06 Hamilton Sundstrand Corporation Thermal and energy management method and apparatus for an aircraft
US6948331B1 (en) * 2003-09-12 2005-09-27 Norhrop Grumman Corporation Environmental control system for an aircraft
US20060005547A1 (en) * 2004-07-09 2006-01-12 David Brouillet Cooling arrangement for an accessory gearbox and method of cooling
US7377100B2 (en) * 2004-08-27 2008-05-27 Pratt & Whitney Canada Corp. Bypass duct fluid cooler
US20070256421A1 (en) * 2006-05-04 2007-11-08 Dooley Kevin A Gas turbine engine oil system operation
US7861512B2 (en) * 2006-08-29 2011-01-04 Pratt & Whitney Canada Corp. Turbofan bypass duct air cooled fluid cooler installation
EP1895124A2 (en) 2006-08-31 2008-03-05 General Electric Company Oil cooling apparatus in fan cowling and method therefor
US20080053099A1 (en) 2006-08-31 2008-03-06 General Electric Company Heat pipe-based cooling apparatus and method for turbine engine
FR2914365A1 (en) 2007-03-28 2008-10-03 Airbus France Sas Equipment e.g. electric generator, cooling and controlling system for propulsion system i.e. jet engine, of aircraft, has closed circuit circulating heat transfer fluid between equipments and two heat exchange units
US20100212857A1 (en) 2007-03-28 2010-08-26 Airbus Operations System for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft
US20090313999A1 (en) 2008-05-13 2009-12-24 Scott Hunter Method and apparatus for controlling fuel in a gas turbine engine
WO2009140100A1 (en) 2008-05-13 2009-11-19 General Electric Company Method and apparatus for controlling fuel in a gas turbine engine
WO2010051011A1 (en) 2008-11-03 2010-05-06 Smith J Walter Systems and methods for thermal management in a gas turbine powerplant
US20100107603A1 (en) 2008-11-03 2010-05-06 Smith J Walter Systems and methods for thermal management in a gas turbine powerplant
US20110252764A1 (en) 2008-11-03 2011-10-20 Propulsion, Gas Turbine, And Energy Evaluations, Llc Systems and methods for thermal management in a gas turbine powerplant
US8522572B2 (en) * 2010-07-01 2013-09-03 General Electric Company Adaptive power and thermal management system
US8967531B2 (en) * 2011-03-28 2015-03-03 Rolls-Royce Corporation Aircraft and airborne electrical power and thermal management system
US8789376B2 (en) * 2011-05-27 2014-07-29 General Electric Company Flade duct turbine cooling and power and thermal management
US9254920B2 (en) * 2012-05-30 2016-02-09 General Electric Company Aircraft energy management system including engine fan discharge air boosted environmental control system
US20140140829A1 (en) * 2012-11-16 2014-05-22 United Technologies Corporation Turbine engine cooling system with an open loop circuit
WO2016156756A1 (en) * 2015-04-03 2016-10-06 Snecma Cooling of a turbine engine oil circuit
US20180050810A1 (en) * 2016-08-19 2018-02-22 General Electric Company Propulsion engine for an aircraft
US20180050811A1 (en) * 2016-08-19 2018-02-22 General Electric Company Propulsion engine for an aircraft

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
International Search Report dated Nov. 15, 2013 in PCT/FR13/051680 filed Jul. 12, 2013.

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200332714A1 (en) * 2019-04-17 2020-10-22 United Technologies Corporation Integrated thermal management system for fuel cooling
US11480105B2 (en) * 2019-04-17 2022-10-25 Raytheon Technologies Corporation Integrated thermal management system for fuel cooling

Also Published As

Publication number Publication date
US20150192033A1 (en) 2015-07-09
GB2519016A (en) 2015-04-08
FR2993610B1 (en) 2014-07-11
GB2519016B (en) 2019-10-16
WO2014013170A1 (en) 2014-01-23
GB201500548D0 (en) 2015-02-25
FR2993610A1 (en) 2014-01-24

Similar Documents

Publication Publication Date Title
US10352190B2 (en) Cooling of an oil circuit of a turbomachine
US20180094584A1 (en) Cooling of the oil circuit of a turbine engine
US9410451B2 (en) Gas turbine engine with integrated bottoming cycle system
JP7134688B2 (en) Intercooled turbine with heat storage system
US20110113781A1 (en) System and method for secondary energy production in a compressed air energy storage system
US20230323814A1 (en) Hydrogen turbine power assisted condensation
CA2777977A1 (en) Flade duct turbine cooling and power and thermal management
CA3074392C (en) A combined heat recovery and chilling system and method
JP2012246928A5 (en)
US10830105B2 (en) System and method for improving output and heat rate for a liquid natural gas combined cycle power plant
JP2015524532A (en) Dual-end drive gas turbine
KR20120026569A (en) Intake air temperature control device and a method for operating an intake air temperature control device
US10954832B2 (en) System for cooling a circuit of a first fluid of a turbomachine
US10794231B2 (en) Reversible system for dissipating thermal power generated in a gas-turbine engine
JP2019507289A5 (en)
CN216581051U (en) Airborne fuel tank inerting device based on integrated thermal management of fuel
WO2014103977A1 (en) Waste heat utilization device for internal combustion engine
JP5675517B2 (en) Gas turbine power generation equipment
US20090293496A1 (en) Gas turbine engines generating electricity by cooling cooling air
CN114180079B (en) Airborne fuel tank inerting method based on fuel oil comprehensive thermal management
US12421888B2 (en) Multi-core heat recovery charge cooler
RU102686U1 (en) POWER AND AIR CONDITIONING GAS-TURBINE UNIT

Legal Events

Date Code Title Description
AS Assignment

Owner name: SNECMA, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GARASSINO, ALAIN PIERRE;DELEPIERRE-MASSUE, OLIVIER ROBERT MICHEL;MISSOUT, MARC;AND OTHERS;REEL/FRAME:034736/0423

Effective date: 20130702

AS Assignment

Owner name: SAFRAN AIRCRAFT ENGINES, FRANCE

Free format text: CHANGE OF NAME;ASSIGNOR:SNECMA;REEL/FRAME:046479/0807

Effective date: 20160803

AS Assignment

Owner name: SAFRAN AIRCRAFT ENGINES, FRANCE

Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME;ASSIGNOR:SNECMA;REEL/FRAME:046939/0336

Effective date: 20160803

STPP Information on status: patent application and granting procedure in general

Free format text: NOTICE OF ALLOWANCE MAILED -- APPLICATION RECEIVED IN OFFICE OF PUBLICATIONS

STPP Information on status: patent application and granting procedure in general

Free format text: PUBLICATIONS -- ISSUE FEE PAYMENT VERIFIED

STCF Information on status: patent grant

Free format text: PATENTED CASE

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 4